The Boeing Company patent applications on December 19th, 2024
Patent Applications by The Boeing Company on December 19th, 2024
The Boeing Company: 41 patent applications
The Boeing Company has applied for patents in the areas of B64D45/00 (4), B64D37/06 (4), B64D37/04 (4), B64D11/00 (3), F17C1/12 (3) F17C1/12 (2), B64D11/0023 (2), B64D37/06 (2), B64C1/1469 (2), G08G5/0021 (1)
With keywords such as: tank, vacuum, configured, pressure, current, portion, end, surface, position, and plate in patent application abstracts.
Patent Applications by The Boeing Company
20240415089. DEVICE FOR LIVE ANIMAL TRANSPORT_simplified_abstract_(the boeing company)
Inventor(s): Jiao Mo of Shanghai (CN) for the boeing company, Ke Ma of Shanghai (CN) for the boeing company, Paola Trapani of Shanghai (CN) for the boeing company, Saverio Silli of Shanghai (CN) for the boeing company, Yiwei Liu of Shanghai (CN) for the boeing company, Jialin Yuan of Shanghai (CN) for the boeing company, Yuchen Tan of Shanghai (CN) for the boeing company, Jiyu Song of Shanghai (CN) for the boeing company, Kudilaiti Kuerban of Shanghai (CN) for the boeing company, Peizhong Gao of Shanghai (CN) for the boeing company, Long Long of Beijing (CN) for the boeing company, Cynthia A. Vandewall of Snohomish WA (US) for the boeing company
IPC Code(s): A01K1/02
CPC Code(s): A01K1/0272
Abstract: the present disclosure relates to a device for live animal transport, comprising: a bottom plate, comprising a liquid guide plate and a non-liquid guide plate, wherein the liquid guide plate has a first end and a second end opposite the first end; a plurality of support members, symmetrically provided at predetermined intervals on the bottom plate at the first end and the second end of the liquid guide plate, and extending in a first direction perpendicular to the bottom plate; a plurality of pillars, one end of each pillar being nested in a corresponding one support member, and the plurality of pillars being capable of telescoping in the first direction; a plurality of beams, extending in a second direction from the first end of the liquid guide plate to the second end of the liquid guide plate, each beam being supported by the other end of the pillar at the first end of the liquid guide plate and the other end of the pillar at the second end of the liquid guide plate; side plates, provided on the bottom plate and extending in the first direction around edges of the bottom plate; and a top portion, supported by the plurality of beams to cover an interior space formed by the bottom plate and the side plates, wherein the plurality of pillars are configured to telescope in the first direction so as to adjust a contour of the top portion
Inventor(s): Tyler Ray Milliken of Charleston SC (US) for the boeing company
IPC Code(s): A62B1/22
CPC Code(s): A62B1/22
Abstract: an inflatable fall protection pad comprises a deformable body defining an inflatable three-dimensional volume. the deformable body has a base wall, an upper wall, and sidewalls spanning the base wall and the upper wall. the inflatable fall protection pad further comprises a set of roller units mounted to the base wall along an exterior-facing surface of the base wall. the set of roller units is arranged in a multi-dimensional array. tw or more roller units of the set are spaced apart from each other in a first dimension of the multi-dimensional array. two or more roller units of the set are spaced apart from each other in a second dimension of the multi-dimensional array that is orthogonal to the first dimension.
Inventor(s): Michael A. Johnson of Kirkland WA (US) for the boeing company, Michael P. Matlack of St. Charles MO (US) for the boeing company, Daniel J. Smolinsky of Mill Creek WA (US) for the boeing company
IPC Code(s): B22D19/00, B22D25/02, B33Y10/00, B33Y80/00
CPC Code(s): B22D19/0072
Abstract: a method for manufacturing a tool having one or more internal channels includes forming one or more channel cores by additive manufacturing, coating a metal onto the one or more channel cores to form a metal tube on each of the one or more channel cores, positioning the one or more metal tubes into a casting mold having a shape of a tool, and casting a molten metal into the casting mold to form the tool having the one or more internal channels corresponding to the one or more channel cores.
Inventor(s): Dale J. Weires of Hockessin DE (US) for the boeing company, Jonathan Venezia of Collegeville PA (US) for the boeing company, Richard K. Kinmonth of Wenonah NJ (US) for the boeing company, Scott M. Holder of Cherry Hill NJ (US) for the boeing company
IPC Code(s): B22F10/62, B22F10/22, B22F10/85, B33Y40/20, B33Y50/02, B33Y70/00, B33Y80/00
CPC Code(s): B22F10/62
Abstract: a method for hardening select portions of a metal article includes establishing a non-reactive atmosphere within a build chamber of an additive manufacturing system, melting a metal material using an energy source to deposit molten material in layers to build the metal article and establishing a reactive atmosphere within the build chamber that causes a chemical reaction to harden a portion of multiple select layers. an additive manufacturing system for hardening select portions of a metal article includes a build chamber, a material handling assembly, a substrate, an energy source assembly, a translational assembly and a system control assembly. a metal article includes layers of a metal material deposited via an additive manufacturing process. a portion of select layers being hardened via a chemical reaction caused by a reactive atmosphere established during periods of the additive manufacturing process.
Inventor(s): Edward John Batt of Boerne TX (US) for the boeing company
IPC Code(s): B23B47/28
CPC Code(s): B23B47/287
Abstract: a drill template includes a tooling plate defining a first aperture extending through the plate along a first axis. the template also includes an adjustable bushing assembly having an outer eccentric element arranged rotatably inside the first aperture and defining a second aperture disposed along a second axis. the template additionally includes an inner eccentric element arranged rotatably inside the second aperture and defining a third aperture disposed along a third axis. the first, second, and third axes are spaced apart from each other. the template also includes a drill bushing arranged inside the third aperture and defining a fourth aperture disposed along a fourth axis. the bushing is configured to swivel relative to the inner eccentric element to orient the fourth aperture relative to the tooling plate. the template further includes a system of fasteners for setting the bushing position relative to the plate for guiding a drill bit.
Inventor(s): Michael Kenneth-Que Louie of Renton WA (US) for the boeing company
IPC Code(s): B29C70/38
CPC Code(s): B29C70/384
Abstract: an automated fiber placement system is provided. the automated fiber placement system comprises a plurality of spools of composite material having a plurality of material widths, each spool of the plurality of spools having a respective material width of the plurality of material widths; and an automated fiber placement head configured to lay up composite tape from any desired spools of the plurality of spools simultaneously.
20240416598. Vacuum Bag Sealing System_simplified_abstract_(the boeing company)
Inventor(s): Michael Kenneth-Que Louie of Renton WA (US) for the boeing company
IPC Code(s): B29C70/44, B29C70/54
CPC Code(s): B29C70/44
Abstract: a vacuum bag sealing system comprises a bagging sheet comprising a sealing surface; a first interlocking strip connected to the sealing surface of the bagging sheet and forming a continuous perimeter connected to the sealing surface; a second interlocking strip between the first interlocking strip and the sealing surface of the bagging sheet in one portion of the perimeter, the second interlocking strip forming a continuous bladder perimeter.
20240416599. Reusable Composite Curing System_simplified_abstract_(the boeing company)
Inventor(s): Michael Kenneth-Que Louie of Renton WA (US) for the boeing company
IPC Code(s): B29C70/44, B29C70/54
CPC Code(s): B29C70/443
Abstract: a reusable composite curing system comprising a reusable bladder; an end fitting sealed to the reusable bladder, the end fitting containing a passage in communication with an interior of the reusable bladder and a first half of the pneumatic connector secured within the end fitting and in communication with the passage; and a cure tool having a venting channel extending from a supporting surface of the cure tool and exiting through one of an underside or a side of the cure tool, and a second half of a pneumatic connector secured within the venting channel; the first half of the pneumatic connector releasable from the second half of the pneumatic connector while maintaining the second half of the pneumatic connector in the cure tool and while maintaining the first half of the pneumatic connector in the end fitting.
Inventor(s): Michael B. Hargett of Charleston SC (US) for the boeing company, Todd M. Vakos of Johns Island SC (US) for the boeing company, Brian Erick Waters of Holly Hill SC (US) for the boeing company
IPC Code(s): B60R16/02, H02G3/32
CPC Code(s): B60R16/0215
Abstract: there is provided a one-piece co-molded snap-on apparatus for supporting one or more elongate elements. the apparatus includes a ring post and a snap-on attachment base co-molded to the ring post for a snap-on attachment to an elongate bar structure. the snap-on attachment base includes a top support portion integral with the ring post, and a bottom attachment portion with side arms opposite each other and designed to snap fit against opposing sides of the elongate bar structure. each side arm has a snap-fit edge portion formed at a bottom end. each snap-fit edge portion has a topmost surface designed to fit against a bottommost surface of the elongate bar structure, and each snap-fit edge portion has a triangular shape and has at least two through openings. at least one centering element projects from an interior surface of the snap-on attachment base into a channel formed between the side arms.
20240417056. Barrier Door for an Aircraft_simplified_abstract_(the boeing company)
Inventor(s): Andrew William Mueller of Mukilteo WA (US) for the boeing company, Christopher Schwitters of Bothell WA (US) for the boeing company
IPC Code(s): B64C1/14, B64D45/00
CPC Code(s): B64C1/1469
Abstract: a barrier door to control movement of persons through an opening within a cabin area of an aircraft. the barrier door includes a body comprising an upper side, a lower side, and lateral sides. a lock is connected to the body and includes an elongated member and a pin. the pin is movable between a disengaged position with a distal end retracted and an engaged position with the distal end extending outward beyond the elongated member. a release mechanism is threaded on the elongated member and is rotatable relative to the elongated member to adjust a position of the elongated member and pin relative to the body.
20240417057. Barrier Door for an Aircraft_simplified_abstract_(the boeing company)
Inventor(s): Darren Carl McIntosh of Mukilteo WA (US) for the boeing company
IPC Code(s): B64C1/14, B64D45/00
CPC Code(s): B64C1/1469
Abstract: a barrier door configured to be mounted in an opening in a cabin area of an aircraft. the barrier door is movable between an open position to allow persons to pass through the opening and a closed position to prevent passengers from moving through the opening. the barrier door is configured to be locked in the closed position.
20240417075. Dual Purpose Lavatory Barrier_simplified_abstract_(the boeing company)
Inventor(s): Darren Carl McIntosh of Mukilteo WA (US) for the boeing company
IPC Code(s): B64D11/00, B64D11/02
CPC Code(s): B64D11/0023
Abstract: a dual purpose aircraft lavatory component that can be a dual purpose aircraft lavatory door that is configured to deploy in a vehicle cabin from an initial position as an aircraft lavatory monument component into a deployed position converting aircraft lavatory monument component into an aircraft cabin lockable barrier to prevent passengers from moving along an aisle in a vehicle cabin into a vehicle area forward of the lockable barrier.
20240417076. Hybrid Barrier for Aircraft Cabin_simplified_abstract_(the boeing company)
Inventor(s): Darren Carl McIntosh of Mukilteo WA (US) for the boeing company
IPC Code(s): B64D11/00, B64D11/04
CPC Code(s): B64D11/0023
Abstract: a hybrid aircraft barrier that is configured to deploy in a vehicle cabin from an initial stowed position as an aircraft cabin monument component into a deployed position converting the aircraft cabin monument component into an aircraft cabin lockable barrier to prevent passengers from moving along an aisle in a vehicle cabin into a vehicle area forward of the lockable barrier.
Inventor(s): Robert E. Grip of Rancho Palos Verdes CA (US) for the boeing company, Aaron J. Kutzmann of Long Beach CA (US) for the boeing company, Nathaniel J. Noel of North Charleston SC (US) for the boeing company
IPC Code(s): B64D37/06, B64D37/04, F17C13/08
CPC Code(s): B64D37/06
Abstract: there is provided a structurally integrated vacuum tank that includes a vacuum tank main portion extending between vacuum tank end portions. the vacuum tank main portion includes a vacuum tank skin forming a cylinder. the vacuum tank skin has a longitudinal cross section with a profile geometry configured for buckling prevention for the vacuum tank skin under external pressure loads. the vacuum tank skin is configured to provide a pressure barrier between an outside ambient pressure and a vacuum in an interior of the vacuum tank main portion. the vacuum tank main portion further includes a plurality of stiffener members coupled to surface portions of the vacuum tank skin. the vacuum tank skin and the plurality of stiffener members are configured to carry structural loads.
Inventor(s): Robert E. Grip of Rancho Palos Verdes CA (US) for the boeing company
IPC Code(s): B64D37/06, B64D37/04, F17C1/02, F17C13/08
CPC Code(s): B64D37/06
Abstract: a tank system includes a vacuum tank and a pressure tank. the vacuum tank has a vacuum tank main portion extending between vacuum tank end portions. the pressure tank is mounted within the vacuum tank, and has a pressure tank main portion extending between pressure tank end portions. the tank system includes a deflection control system comprising at least one elongate support member extending from a vacuum tank first side of the vacuum tank main portion, and passing through an opening in a pressure tank first side of the pressure tank main portion, and coupled to a pressure tank second side opposite the pressure tank first side. the elongate support member is configured to support the pressure tank main portion and reduce deflections of the pressure tank main portion relative to the vacuum tank main portion when the tank system is subjected to a load.
Inventor(s): Darren Carl McIntosh of Mukilteo WA (US) for the boeing company
IPC Code(s): B64D11/00, B64D11/06
CPC Code(s): B64D45/0026
Abstract: a deployable attendant seat assembly that is configured to deploy in a vehicle cabin from a stowed position as an attendant seat into a deployed position configuring the deployable attendant seat assembly into a lockable barrier to prevent passengers from moving along an aisle in a vehicle cabin into a vehicle area forward of the lockable barrier.
20240417109. ACCOUNTING FOR INERTIAL MEASUREMENT UNIT BIAS_simplified_abstract_(the boeing company)
Inventor(s): Andrew WALSH of Redondo Beach CA (US) for the boeing company, Reid REYNOLDS of Huntsville AL (US) for the boeing company
IPC Code(s): B64G1/28, B64G1/24, B64G1/26, B64G1/36, G01P21/02
CPC Code(s): B64G1/28
Abstract: techniques for accounting for rotational bias of an inertial measurement unit in a setting where momentum is conserved are presented. the techniques include: obtaining, from an inertial measurement unit, an initial magnitude of momentum and initial directional rotational rates; iteratively updating an estimate of bias of magnitude of momentum and estimates of bias of directional rotational rates based at least on the obtaining and based at least on readings from the inertial measurement unit; adjusting directional rotational rates obtained from the inertial measurement unit to account for the estimates of bias of directional rotational rates, where bias adjusted directional rotational rates are determined; and providing the bias adjusted directional rotation rates.
20240417515. SCHIFF BASE OLIGOMERS_simplified_abstract_(the boeing company)
Inventor(s): Andrew M. ZWEIG of Akron OH (US) for the boeing company, Waynie M. SCHUETTE of Troy IL (US) for the boeing company
IPC Code(s): C08G75/00
CPC Code(s): C08G75/00
Abstract: aspects of the present disclosure relate to schiff base oligomers and uses thereof. in at least one aspect, an oligomer is represented by formula (iv) wherein each instance of ris independently selected from the group consisting of alkyl, cycloalkyl, aryl, heteroaryl, and ether. each instance of rand rof formula (iv) is independently selected from the group consisting of hydrogen, alkyl, cycloalkyl, and aryl. each instance of rof formula (iv) is independently selected from the group consisting of alkyl, cycloalkyl, aryl, heterocyclyl, and a bond. each instance of rof formula (iv) is independently —nh— or a bond and each instance of ris independently —nh— or —nh—nh—. each instance of rof formula (iv) is independently —nh— or a bond and each instance of ris independently —nh— or —nh—nh—.
Inventor(s): Malia ZEE of St. Louis MO (US) for the boeing company, Angela Christine Faith DAVIS of Maryland Heights MO (US) for the boeing company, Karen Ann SCHULTZ of Seattle WA (US) for the boeing company, Kay Youngdahl BLOHOWIAK of Issaquah WA (US) for the boeing company, Jill Elisabeth SEEBERGH of Seattle WA (US) for the boeing company, Eric Alan BRUTON of Lake Saint Louis MO (US) for the boeing company, Weidong YANG of Clayton (AU) for the boeing company, Sheng LI of Melbourne (AU) for the boeing company, Ranya SIMONS of Melbourne (AU) for the boeing company, Nick RIGOPOULOS of Brighton (AU) for the boeing company
IPC Code(s): C09D5/00, C09D7/20, C09D7/40, C09D7/61, C09D7/63, C09D183/08, C09J5/02, C09J5/06, C09J5/10
CPC Code(s): C09D5/002
Abstract: an adhesion promoter composition is including one or more reactive silanes, one or more swelling agents, and one or more organic solvents, where the one or more reactive silanes forms a complex with the one or more swelling agents is disclosed. the one or more reactive silanes may include an amine functional group, an epoxy functional group, a mercapto functional group, an isocyanate functional group, or a combination thereof. the one or more swelling agents is selected from a group which may include phenol or naphthol derivatives. a composite part including the adhesion promoter composition and a method for applying the adhesion promoter composition is also disclosed.
Inventor(s): Thomas K. Tsotsis of Santa Ana CA (US) for the boeing company
IPC Code(s): D06M11/74, D06B3/10, D06M10/06, D06M11/46, D06M11/77, D06M11/80, D06M23/08
CPC Code(s): D06M11/74
Abstract: a fabricating method is provided for a multilayered, nanoparticle-coated fiber material using a layer-by-layer nanoparticle-deposition system. fabrication includes coating a fiber substrate with a first type of nanoparticle to provide a first coated layer of the multilayered, nanoparticle-coated fiber material. fabrication also includes coating the first coated layer with a second type of nanoparticle to provide a second coated layer of the multilayered, nanoparticle-coated fiber material.
Inventor(s): Farahnaz Sisco of Mukilteo WA (US) for the boeing company, Nathan A. Muntz of Everett WA (US) for the boeing company, Blake A. Simpson of Kirkland WA (US) for the boeing company
IPC Code(s): F16B1/00
CPC Code(s): F16B1/00
Abstract: a fastening system includes a plurality of groups of fasteners. each group includes a plurality of identical fasteners. each fastener includes a fastener body and a coating applied to at least a portion of the fastener body. the coating includes a binder and a colorant. each group of fasteners has a specific structural characteristic that differs between the groups, and each group of fasteners has a distinct color represented by a set of cie lab coordinates (l, a, b).
Inventor(s): Robert E. Grip of Rancho Palos Verdes CA (US) for the boeing company, Aaron J. Kutzmann of Long Beach CA (US) for the boeing company, Nathaniel J. Noel of North Charleston SC (US) for the boeing company
IPC Code(s): F17C1/12, B64C1/06, B64D37/04, B64D37/06, B64D37/30, F17C13/00
CPC Code(s): F17C1/12
Abstract: there is provided a segmented vacuum jacketed tank system. the system includes a segmented structurally integrated vacuum tank having a vacuum tank main portion between vacuum tank end portions. the vacuum tank main portion includes a vacuum tank skin having an outer surface and an inner surface, vacuum tank skin segments, and a longitudinal cross section with a profile geometry configured for buckling prevention for the vacuum tank skin under external pressure loads. the vacuum tank main portion includes multipurpose stiffener member(s) configured to carry one or more of system transport line(s), a liquid fuel, or a nitrogen gas in an interior. the system includes a pressure tank within the segmented structurally integrated vacuum tank. the pressure tank is configured to store a cryogenic fluid and includes a pressure tank main portion between pressure tank end portions. the system further includes a vacuum cavity.
Inventor(s): Robert E. Grip of Rancho Palos Verdes CA (US) for the boeing company, Aaron J. Kutzmann of Long Beach CA (US) for the boeing company
IPC Code(s): F17C1/12, B64D37/04, B64D37/06, F17C13/00
CPC Code(s): F17C1/12
Abstract: a tank system includes a vacuum tank having a vacuum tank skin, and a pressure tank mounted within the vacuum tank having one or more pressure tank skin segments having a total circumference that is less than that of a complete circle, resulting in one or more longitudinal gaps respectively between the one or more pressure tank skin segments. the tank system includes one or more gap control mechanisms configured to control a width of the one or more longitudinal gaps in a manner facilitating movement of the one or more pressure tank skin segments between at least the following positions: a retracted position in which there is a radial gap between each pressure tank skin segment and the vacuum tank skin, and a fully extended position in which at least a portion of each pressure tank skin segments is in contact with the vacuum tank skin.
Inventor(s): Robert E. Grip of Rancho Palos Verdes CA (US) for the boeing company, Aaron J. Kutzmann of Long Beach CA (US) for the boeing company
IPC Code(s): F17C13/12, F17C1/12
CPC Code(s): F17C13/12
Abstract: there is provided a tank system having a removable plug assembly. the tank system has a vacuum tank with a vacuum tank main portion, a pressure tank mounted within the vacuum tank, and a vacuum cavity formed between the pressure tank and the vacuum tank. the pressure tank has the removable plug assembly with removable plug element(s), each configured to plug and to unplug opening(s) in the pressure tank, and a retraction mechanism within the pressure tank coupled to the removable plug element(s). when an emergency condition occurs, the retraction mechanism is activated to pull the removable plug element(s) away from the opening(s) and into the interior of the pressure tank, to allow a cryogenic fluid to exit from the pressure tank, through the opening(s), and into the vacuum cavity, and when the vacuum tank has a breach, to allow the cryogenic fluid to further exit out into air.
20240418512. MULTI-SEGMENT PRECISION CLOSED-LOOP CONTROL_simplified_abstract_(the boeing company)
Inventor(s): Richard PEPE of Redondo Beach CA (US) for the boeing company, Andrew WALSH of Redondo Beach CA (US) for the boeing company, Reid REYNOLDS of Huntsville AL (US) for the boeing company
IPC Code(s): G01C21/24, G05D1/46
CPC Code(s): G01C21/24
Abstract: techniques for maneuvering a space vehicle are presented. the techniques can include: obtaining a representation, in a computer, of a multi-segment planned position, planned velocity, and planned acceleration of the space vehicle along a planned continuous trajectory; tracking, using at least one navigation sensor, an indication of an actual position, actual velocity, and actual acceleration of the space vehicle; and maneuvering the space vehicle, using a closed-loop controller, and based on the tracking, to return to the planned position, planned velocity, and planned acceleration.
20240418745. Wheel Speed Transducer Test Adapter_simplified_abstract_(the boeing company)
Inventor(s): Matthew Norris Mellon of Payson IL (US) for the boeing company, Joseph Edward Flach of St. Charles MO (US) for the boeing company
IPC Code(s): G01P21/00, B64F5/60
CPC Code(s): G01P21/00
Abstract: a wheel speed transducer test adapter and method for wheel speed transducer testing. the wheel speed transducer test adapter includes a socket for engagement with a wheel hub. a clevis is rotatable within the socket and with respect to the socket and the wheel hub. the clevis is engaged with a wheel speed transducer attached to the wheel hub. a collar secures the clevis to the socket. a torque supplying device rotates the clevis at a consistent speed which in turn rotates the wheel speed transducer to test the wheel speed transducer after repair or replacement. the entire assembly ensures stability and alignment while the clevis and wheel speed transducer rotate.
20240418762. Diagnostic Circuit_simplified_abstract_(the boeing company)
Inventor(s): Ian M. Dayton of Arlington VA (US) for the boeing company, Mark Edward Nowakowski of Arlington VA (US) for the boeing company
IPC Code(s): G01R29/26
CPC Code(s): G01R29/26
Abstract: a diagnostic circuit includes a superconducting quantum interference device (squid) configured to be coupled to a test circuit such that an electronic noise present in the test circuit induces a first current that flows through the squid. the diagnostic circuit also includes a current path configured to receive a second current that flows through the squid. the squid is configured to generate an output in a form of: a first voltage in response to a sum of the first current and the second current being less than a threshold current and a second voltage in response to the sum of the first current and the second current being greater than the threshold current.
20240418773. Diagnostic Device_simplified_abstract_(the boeing company)
Inventor(s): Ian M. Dayton of Arlington VA (US) for the boeing company, Mark Edward Nowakowski of Arlington VA (US) for the boeing company
IPC Code(s): G01R31/3185, G06F1/20
CPC Code(s): G01R31/2887
Abstract: a diagnostic device includes a probe, a motor configured to scan the probe over a test circuit, a superconducting quantum interference device (squid) attached to the probe and configured to be coupled to the test circuit such that an electronic noise present in the test circuit induces a first current that flows through the squid, and a current path configured to receive a second current that flows through the squid. the squid is configured to generate an output in a form of a first voltage in response to a sum of the first current and the second current being less than a threshold current, and a second voltage in response to the sum of the first current and the second current being greater than the threshold current.
20240418802. Diagnostic Apparatus_simplified_abstract_(the boeing company)
Inventor(s): Ian M. Dayton of Arlington VA (US) for the boeing company, Mark Edward Nowakowski of Arlington VA (US) for the boeing company
IPC Code(s): G01R33/035, H05K7/20
CPC Code(s): G01R33/0354
Abstract: a diagnostic apparatus includes a first array of superconducting quantum interference devices (squids). each squid of the first array is configured to be coupled respectively to a test circuit of a second array of test circuits such that an electronic noise present in the test circuit induces a first current that flows through the squid. the diagnostic apparatus also includes a current source configured to provide a second current for each squid of the first array such that the second current flows through the squid. each squid of the first array is configured to generate an output in a form of: a first voltage in response to a sum of the first current and the second current being less than a threshold current, and a second voltage in response to the sum of the first current and the second current being greater than the threshold current.
Inventor(s): Jason Andrew Miller of Austin TX (US) for the boeing company, Christopher Tyson Weihs of Houston TX (US) for the boeing company, Kathryn Bauer Thomas of Portland ME (US) for the boeing company, Malcolm Toon of Cape Elizabeth ME (US) for the boeing company
IPC Code(s): G01W1/10, B64D43/00, G01W1/00
CPC Code(s): G01W1/10
Abstract: systems and methods are provided for graphically presenting aviation-focused weather information. one exemplary method comprises receiving weather information for a select geographic location and a select time period, the select time period comprising a plurality of consecutive days, each day comprising a plurality of consecutive hours, and the weather information comprising aviation-specific weather conditions associated with the select time period; and displaying a graphical user interface configured to graphically present the aviation-specific weather conditions using a plurality of graphical elements in a first region of the graphical user interface, each graphical element corresponding to a respective one of the consecutive calendar days and each aviation-specific weather condition having an assigned color-coding or shading, wherein each graphical element is configured to graphically depict the aviation-specific weather condition for each hour of the corresponding calendar day using the assigned color-coding or shading.
Inventor(s): Ryan King-Shepard of Somerville MA (US) for aurora flight sciences corporation, a subsidiary of the boeing company
IPC Code(s): G05D1/00, G05D1/43, G05D1/46, G05D1/81
CPC Code(s): G05D1/0202
Abstract: a method is provided for detecting and avoiding conflict during a mission of a robot that includes a global route of travel. the method includes monitoring a state of the robot and a state of an environment of the robot as the robot travels the global route. the method includes generating a local route of travel through a region of the environment that includes the robot, the region having a size and shape that are set based on a type of the robot and the state of the robot when the local route is generated. a measure of uncertainty in the perception of objects in the region is monitored based on the state of the environment. and the robot is caused to maintain the global route or transition to the local route based on a comparison of the measure of uncertainty and an uncertainty threshold.
Inventor(s): Marco Gaertner of Sinntal-Sannerz (DE) for the boeing company, Ralf Rene Cabos of Hainburg (DE) for the boeing company
IPC Code(s): G06F16/215, G06N20/00
CPC Code(s): G06F16/215
Abstract: apparatuses, methods, systems, and program products are disclosed for dynamic selection of an aeronautical data provider. an apparatus includes a processor and a memory that stores code executable by the processor to receive streams of aeronautical data from a plurality of aeronautical data providers streaming aeronautical data from different geographic locations, determine a quality of each of the received streams of aeronautical data by checking the aeronautical data against data provided by at least one secondary data source that has a known quality, select an aeronautical data provider of the plurality of aeronautical data providers that provides a stream of aeronautical data that is closest to the data provided by the at least one secondary data source, and expose aeronautical data from the stream of aeronautical data of the selected aeronautical data provider to an end user according to one or more parameters.
Inventor(s): John Makoto Shinozaki of Kenmore WA (US) for the boeing company
IPC Code(s): G06F30/10
CPC Code(s): G06F30/10
Abstract: manufacturing analysis is provided. the method comprises identifying a feature of a product model defined by geometric, physical, and systems elements with semantic labels, names or title descriptions. machine readable semantic links are created that connect the feature to elements in an enterprise knowledge library according to a machine readable ontological knowledge model. a producibility risk or opportunity for the product model is identified according to semantic relationships of the elements in the enterprise knowledge library linked to the feature. a user is alerted of the producibility risk or opportunity, and a note is added to a manufacturing design specification for the product model. the note provides a number of solutions for the producibility risk or opportunity, wherein the solutions are identified in the enterprise knowledge library according to the semantic relationships.
Inventor(s): Caleb G. Price of Hazelwood MO (US) for the boeing company, Jeffrey H. Hunt of El Segundo CA (US) for the boeing company
IPC Code(s): G06T5/92, B64D47/08, B64U101/30, G06T5/40, G06T5/50, G06V10/50, H04N23/71, H04N23/76
CPC Code(s): G06T5/92
Abstract: a computer vision method performed by a computing system includes: receiving an image; identifying a light intensity value for each pixel of a set of pixels of the image; defining a light intensity band formed by an upper light intensity threshold and a lower light intensity threshold based on a light intensity distribution of the light intensity values of the set of pixels; for each pixel of the set of pixels, identifying whether that pixel has a light intensity value that is within the light intensity band or outside of the intensity band; and generating a modified image by increasing a light intensity contrast between a first subset of pixels identified as having light intensity values within the light intensity band and a second subset of pixels identified as having light intensity values outside of the light intensity band.
Inventor(s): Andreas Bartl of Munich (DE) for the boeing company, Seth A. Yakel of Seattle WA (US) for the boeing company, Kwok Tung Chan of Mercer Island WA (US) for the boeing company
IPC Code(s): G06T7/00, G06T3/40, G06T7/11
CPC Code(s): G06T7/0008
Abstract: an inspection system includes a scanner and a computing device. the scanner is configured to scan an inner surface of a hole in an object. the scanner is configured to generate a plurality of images. each one of the images represents one of a plurality of sections of the inner surface of the hole. the computing device is coupled to the scanner to receive the plurality of images. the computing device is programmed to combine the plurality of images to form an image. the image represents the inner surface of the hole. the computing device is programmed to evaluate a surface characteristic of the inner surface based on pixel-intensity values of the image.
Inventor(s): Yang Chen of Westlake Village CA (US) for the boeing company, Deepak Khosla of Camarillo CA (US) for the boeing company, Brandon Michael Courter of Indianapolis IN (US) for the boeing company, Jeremy Daniel Howe of Everett WA (US) for the boeing company, Shane Edward Arthur of Kirkland WA (US) for the boeing company, Anders Eirik Heussy of Seattle WA (US) for the boeing company
IPC Code(s): G06V10/774, G06T7/20, G06V10/776
CPC Code(s): G06V10/774
Abstract: a method of generating a detector is disclosed herein. the method includes obtaining a first training dataset including a first set of tagged images identifying a first object and obtaining a second training dataset including a second set of tagged images identifying a second object. a first parts-level detector is trained based on the first training dataset and a second parts-level detector is trained based on the second training dataset. a unified detector is trained based on the first training dataset and the second training dataset.
20240420471. METHOD AND SYSTEM FOR PROCESS MONITORING_simplified_abstract_(the boeing company)
Inventor(s): Yang Chen of Westlake Village CA (US) for the boeing company, Deepak Khosla of Camarillo CA (US) for the boeing company, Brandon Michael Courter of Indianapolis IN (US) for the boeing company, Shane Edward Arthur of Kirkland WA (US) for the boeing company, Jeremy Daniel Howe of Everett WA (US) for the boeing company, Anders Eirik Heussy of Seattle WA (US) for the boeing company
IPC Code(s): G06V20/52, G06T7/20, G06V10/25, G06V20/40
CPC Code(s): G06V20/52
Abstract: a method of monitoring an assembly process is disclosed herein. the method includes obtaining an event model for each of a plurality of objects in the assembly process with the event model for each of the plurality of objects including a predetermined time frame for a change in presence to occur. the method includes collecting an image sequence of the assembly process for monitoring and identifying if a change in presence for each of the plurality of objects occurred with a detector model. the method further includes reviewing the event model for each of the plurality of objects to determine if the predetermined time frame lapsed without the change in presence of a corresponding one of the plurality of objects being identified and issuing an alert if the predetermined time frame lapsed without the presence of a corresponding one of the plurality of objects being identified.
Inventor(s): Richard John Loftis of Charleston SC (US) for the boeing company, David Richard Bowman of Charleston SC (US) for the boeing company, Cedar Frost of Marysville WA (US) for the boeing company
IPC Code(s): G08G5/00
CPC Code(s): G08G5/0004
Abstract: methods of operating radio frequency identification (rfid) devices on a vehicle. the methods include determining a geographic location of the vehicle. based on the geographic location of the vehicle, determining an operational requirement for the rfid devices. after determining the operational requirement, operating the rfid devices according to the operational requirement. the methods provide for operating the rfid devices within compliance for the operational requirements that are required in the different geographic locations where the vehicle travels.
Inventor(s): Ajaya Srikanta Bharadwaja of Bangalore (IN) for the boeing company, Chaitra Jagadeesh of Bangalore (IN) for the boeing company
IPC Code(s): G08G5/00
CPC Code(s): G08G5/0021
Abstract: a system and a method include a control unit configured to determine situational information regarding a plurality of aircraft within an airspace. the control unit is configured to determine the situational information based on automatic dependent surveillance-broadcast (ads-b) signals output by the plurality of aircraft and received by an ads-b receiver of a tracking sub-system.
Inventor(s): James Y. Lee of La Habra CA (US) for the boeing company, Li C. Chang of Mt. Pleasant SC (US) for the boeing company
IPC Code(s): H02K35/02, B64D45/00, G01M7/02
CPC Code(s): H02K35/02
Abstract: a kinetic-energy harvester and associated acoustic detection system and method are disclosed. the kinetic-energy harvester includes a magnet with a coil-facing surface and a coil array including a plurality of conductive coils. the coil array is offset from the magnet in a first direction, such that an air gap is defined between the coil-facing surface of the magnet and the coil array. a cantilever beam spring couples the magnet to the coil array and is configured to enable movement of the coil array, relative to the magnet, about a vibration axis that is perpendicular to the first direction. the kinetic-energy harvester is configured to harvest electrical power from vibrations of a vibration-generating object and transmit the electrical power to a system, such as an acoustic detection system which is configured to detect acoustic signals in the vibration-generating object and convert into acoustic data.
Inventor(s): James Y. Lee of La Habra CA (US) for the boeing company, Li C. Chang of Mt. Pleasant SC (US) for the boeing company
IPC Code(s): H02N2/18, B64D45/00, B81B3/00, G01H1/14, G01H1/16, H02J50/00, H02K35/02
CPC Code(s): H02N2/186
Abstract: an acoustic detection system and method and associated kinetic energy harvester is disclosed. the acoustic detection system comprises a vibration-generating object, a kinetic-energy harvester, and an acoustic sensor. the kinetic-energy harvester is embedded within a first location of the vibration-generation object and is configured to wirelessly transmit electrical power to the acoustic sensor, which is embedded within a second location of the vibration-generating object. the acoustic sensor is configured to receive the electrical power, detect acoustic signals, and convert the detected acoustic signals into acoustic data. the kinetic energy harvester may be an electromagnetic harvester that comprises a magnet array and a coil array comprising at least one conductive coil. by inducing a current in the at least one conductive coil through the relative motion between the magnet array and the coil array, the kinetic-energy harvester produces electrical power.
20240423104. Nanowire Avalanche Photodetector_simplified_abstract_(the boeing company)
Inventor(s): Brett Alexander Yurash of Venice CA (US) for the boeing company
IPC Code(s): H10N60/84, H10N60/82, H10N60/83
CPC Code(s): H10N60/84
Abstract: a nanowire photodetection system comprising an optical waveguide and superconducting nanowires. the optical waveguide is located on a substrate. the superconducting nanowires are electrically connected in parallel to connector wires located on both sides of the optical waveguide. a set of the superconducting nanowires cross a width of the optical waveguide and absorb a photon in the optical waveguide.
The Boeing Company patent applications on December 19th, 2024
- The Boeing Company
- A01K1/02
- CPC A01K1/0272
- The boeing company
- A62B1/22
- CPC A62B1/22
- B22D19/00
- B22D25/02
- B33Y10/00
- B33Y80/00
- CPC B22D19/0072
- B22F10/62
- B22F10/22
- B22F10/85
- B33Y40/20
- B33Y50/02
- B33Y70/00
- CPC B22F10/62
- B23B47/28
- CPC B23B47/287
- B29C70/38
- CPC B29C70/384
- B29C70/44
- B29C70/54
- CPC B29C70/44
- CPC B29C70/443
- B60R16/02
- H02G3/32
- CPC B60R16/0215
- B64C1/14
- B64D45/00
- CPC B64C1/1469
- B64D11/00
- B64D11/02
- CPC B64D11/0023
- B64D11/04
- B64D37/06
- B64D37/04
- F17C13/08
- CPC B64D37/06
- F17C1/02
- B64D11/06
- CPC B64D45/0026
- B64G1/28
- B64G1/24
- B64G1/26
- B64G1/36
- G01P21/02
- CPC B64G1/28
- C08G75/00
- CPC C08G75/00
- C09D5/00
- C09D7/20
- C09D7/40
- C09D7/61
- C09D7/63
- C09D183/08
- C09J5/02
- C09J5/06
- C09J5/10
- CPC C09D5/002
- D06M11/74
- D06B3/10
- D06M10/06
- D06M11/46
- D06M11/77
- D06M11/80
- D06M23/08
- CPC D06M11/74
- F16B1/00
- CPC F16B1/00
- F17C1/12
- B64C1/06
- B64D37/30
- F17C13/00
- CPC F17C1/12
- F17C13/12
- CPC F17C13/12
- G01C21/24
- G05D1/46
- CPC G01C21/24
- G01P21/00
- B64F5/60
- CPC G01P21/00
- G01R29/26
- CPC G01R29/26
- G01R31/3185
- G06F1/20
- CPC G01R31/2887
- G01R33/035
- H05K7/20
- CPC G01R33/0354
- G01W1/10
- B64D43/00
- G01W1/00
- CPC G01W1/10
- G05D1/00
- G05D1/43
- G05D1/81
- CPC G05D1/0202
- Aurora flight sciences corporation, a subsidiary of the boeing company
- G06F16/215
- G06N20/00
- CPC G06F16/215
- G06F30/10
- CPC G06F30/10
- G06T5/92
- B64D47/08
- B64U101/30
- G06T5/40
- G06T5/50
- G06V10/50
- H04N23/71
- H04N23/76
- CPC G06T5/92
- G06T7/00
- G06T3/40
- G06T7/11
- CPC G06T7/0008
- G06V10/774
- G06T7/20
- G06V10/776
- CPC G06V10/774
- G06V20/52
- G06V10/25
- G06V20/40
- CPC G06V20/52
- G08G5/00
- CPC G08G5/0004
- CPC G08G5/0021
- H02K35/02
- G01M7/02
- CPC H02K35/02
- H02N2/18
- B81B3/00
- G01H1/14
- G01H1/16
- H02J50/00
- CPC H02N2/186
- H10N60/84
- H10N60/82
- H10N60/83
- CPC H10N60/84
